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Shock and Vibration
Volume 2015 (2015), Article ID 136026, 11 pages
http://dx.doi.org/10.1155/2015/136026
Research Article

Numerical Investigation of Flapwise-Torsional Vibration Model of a Smart Section Blade with Microtab

1School of Hydraulic, Energy and Power Engineering, Yangzhou University, Yangzhou, Jiangsu 225127, China
2Aerospace Engineering, Embry-Riddle Aeronautical University, Daytona Beach, FL 32114-3900, USA
3Wright State Research Institute, AFRL RQVC, Beavercreek, OH 45431, USA

Received 16 April 2015; Revised 19 July 2015; Accepted 27 July 2015

Academic Editor: Peng Chen

Copyright © 2015 Nailu Li et al. This is an open access article distributed under the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.

Abstract

This study presents a method to develop an aeroelastic model of a smart section blade equipped with microtab. The model is suitable for potential passive vibration control study of the blade section in classic flutter. Equations of the model are described by the nondimensional flapwise and torsional vibration modes coupled with the aerodynamic model based on the Theodorsen theory and aerodynamic effects of the microtab based on the wind tunnel experimental data. The aeroelastic model is validated using numerical data available in the literature and then utilized to analyze the microtab control capability on flutter instability case and divergence instability case. The effectiveness of the microtab is investigated with the scenarios of different output controllers and actuation deployments for both instability cases. The numerical results show that the microtab can effectively suppress both vibration modes with the appropriate choice of the output feedback controller.